EP0869272B1 - Inverseur de poussée protégé au déverrouillage pour turbomoteur d'aéronef - Google Patents

Inverseur de poussée protégé au déverrouillage pour turbomoteur d'aéronef Download PDF

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Publication number
EP0869272B1
EP0869272B1 EP98400775A EP98400775A EP0869272B1 EP 0869272 B1 EP0869272 B1 EP 0869272B1 EP 98400775 A EP98400775 A EP 98400775A EP 98400775 A EP98400775 A EP 98400775A EP 0869272 B1 EP0869272 B1 EP 0869272B1
Authority
EP
European Patent Office
Prior art keywords
hook
free end
latch
tie
closed position
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP98400775A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0869272A1 (fr
Inventor
Pierre André Marcel Baudu
Patrick Gonidec
Guy Bernard Vauchel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Nacelles Ltd
Original Assignee
Hurel Hispano SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hurel Hispano SA filed Critical Hurel Hispano SA
Publication of EP0869272A1 publication Critical patent/EP0869272A1/fr
Application granted granted Critical
Publication of EP0869272B1 publication Critical patent/EP0869272B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • E—FIXED CONSTRUCTIONS
    • E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
    • E05C—BOLTS OR FASTENING DEVICES FOR WINGS, SPECIALLY FOR DOORS OR WINDOWS
    • E05C3/00—Fastening devices with bolts moving pivotally or rotatively
    • E05C3/12—Fastening devices with bolts moving pivotally or rotatively with latching action
    • E05C3/16—Fastening devices with bolts moving pivotally or rotatively with latching action with operating handle or equivalent member moving otherwise than rigidly with the latch
    • E05C3/22—Fastening devices with bolts moving pivotally or rotatively with latching action with operating handle or equivalent member moving otherwise than rigidly with the latch the bolt being spring controlled
    • E05C3/24—Fastening devices with bolts moving pivotally or rotatively with latching action with operating handle or equivalent member moving otherwise than rigidly with the latch the bolt being spring controlled in the form of a bifurcated member
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/76—Control or regulation of thrust reversers
    • F02K1/766—Control or regulation of thrust reversers with blocking systems or locking devices; Arrangement of locking devices for thrust reversers

Definitions

  • the invention relates to thrust reversers of the so-called type "with doors” for aircraft turbine engine, and more particularly to an improvement allowing the door retention in the event of damage to the inverter resulting for example from the bursting of a disc of the turbine engine.
  • Thrust reversers for aircraft turbine engines are well-known devices making it possible to refer to forward the propellant air flow generated by the turbine engine, to reduce the speed of the aircraft.
  • a thrust reverser of the so-called "door type” is a structure thin and light ring surrounding the turbine engine and made usually sheet metal.
  • the inverter usually has a fixed structure itself comprising a "front frame” and a “rear frame” both of annular shape surrounding the turboshaft engine, a plurality of substantially parallel beams connecting the rear frame to the front frame, and a plurality radial openings.
  • the inverter also has doors swivel whose function is to ensure closure of said openings, or else to forward the flow propelling air passing through the openings when the doors are open.
  • the inverter also includes control devices for opening and closing doors, as well as devices for locking said doors in position closed.
  • a locking device comprises usually a lock secured to the fixed structure, the more often of the front frame, said lock cooperating with a element at the front of the door to keep closed, this element usually in the form of a tie rod one end is integral with the door and the other of which end is free and gripped by the lock (see for example document EP-A-656,469).
  • tie rods can obviously take very variable forms. For convenience of language, we will call in what follows “free end of the tie rod” the door element with which cooperates the lock to hold said door in position closed.
  • front of the door we will also designate well the actual front of the door as the front side faces of said doors.
  • doors of a thrust reverser are "self-opening", that is to say that they tend to open under the pressure of the propellant gases generated by the turbine engine, this being obtained by door pivots deported to the rear of said doors. Doors can also be “self-closing”, ie they tend to close under the effect of propellant gas pressure generated by the turbine engine, the door pivots being in this cases deported to the front of said doors.
  • the bolt of a reverser door lock thrust is a moving member that is very stressed during operation normal, and even more stressed in case of damage to the structure of the inverter.
  • the reduction of said solicitations is therefore an advantage.
  • the invention proposes have on the assembly constituted by the fixed structure and the door latch a hook surrounding the free end of the pulling from the door in the closed position, said hook having an opening through which the free end passes of the tie rod when it reaches its closed position, said opening being obscured by the bolt of the bolt in position closed.
  • the hook can be placed directly on the structure fixed. However, in a preferred embodiment, the hook will be placed on the lock body. This allows hold the hook by means of the bolt, which avoids to have to have additional means of connection on inverter.
  • the invention can then be applied to existing inverters without modification of said inverters, by simply replacing the existing lock.
  • a housing at least the size of the free end of the pulling.
  • This housing has the function of receiving the end free of the tie in the event of deformation of the fixed structure, which then retains the door with the end free of said hook which will consequently undergo the effort of retention of the door in place of the bolt of the lock, thereby relieving said bolt of said retention effort.
  • one side can be arranged on the hook support opposite the free end of the door pull, this bearing face being substantially parallel to the trajectory of said free end in the vicinity of the closed position, this bearing face being turned towards the lock body.
  • the bearing face according to the invention has the function of oppose the release of the free end of the tie rod and minimize the reaction force exerted by the free end of the bolt in the event of deformation of the structure fixed, said free end bearing on the hook.
  • the bottom of the hook i.e. its part against the latch and opposite the opening, can be positioned at the end of the stroke of the free end of the tie rod and thus constitute a stop limiting the travel of said free end of the pulling, in order to release the bolt from the bolt of this function, which reduces the efforts it has to bear.
  • the hook will be pivotably mounted on the lock body in order to ability to at least partially close opening of said opening hook, this hook being simultaneously pulled into position closed by a spring and kept in the open position by a thermally fusible link with the body of the lock.
  • the connection is broken by fusion, which releases the hook which closes under the effect of traction of the spring, said hook then holding the end of the pulling trapped against the bolt even when opened accidental lock, which makes it impossible to open door in the event of fire.
  • Figure 1 illustrates the structure of a thrust reverser of the so-called "door” type on which the features of the invention.
  • FIG. 2 illustrates an example of implementation of the invention.
  • Figure 3 illustrates a particular form of implementation of the invention in which the hook has a face support.
  • Figure 4 illustrates a particular form of implementation of the invention in which the hook also ensures the limit stop function.
  • Figure 5 illustrates a hook split and reinforced by side cheeks. For clarity, only one tie was represented.
  • Figure 6 illustrates a split hook, reinforced with cheeks lateral and bridged at its free end.
  • Figure 7 illustrates a particular form of the invention in which the hook is pivotally mounted and linked to the body of the lock by a thermally fusible element.
  • the thrust reverser being substantially circular according to a horizontal geometric axis, and the doors being oriented at different angles because they are distributed on the circumference of the inverter, we will designate for simplify the description by the term high and its equivalents which is outward from the inverter and by the term low and its equivalents which is towards the center of inverter.
  • the inverter of thrust 1 has a general form of revolution surrounding the turboshaft not shown.
  • the thrust reverser 1 comprises first a fixed structure 2 composed essentially of a front frame 3 and a rear frame 4 both of form annular, as well as a plurality of non-beams shown connecting the front frame 3 and the rear frame 4.
  • the fixed structure 2 is internally delimited by a inner wall 6 channeling the propellant gas flow 7 generated by the turbine engine not shown, as well as by a outer wall 8 against which the ambient air 9 flows during the flight of the aircraft.
  • the fixed structure 2 is also traversed radially by a plurality of openings 10 concealed by doors 11 each having a wall inner 12 and an outer wall 13 which are respectively in alignment with the inner wall 6 and of the outer wall 8 of the fixed structure 2.
  • the door 11 is pivotally mounted on the fixed structure 2 by the pivots 14 and is actuated in the open or closed position by a door jack 15, one end of which is connected to the door 11 by a joint 16 while its other end is connected to the front frame 3 by a ball joint 17.
  • the door 11 is held in the closed position by a device lock 20 which provides the mechanical connection of at least point 21 of gate 11 to at least point 22 of fixed structure 2.
  • the connection point 21 on the door 11 is at the end front of said door 11, and point 22 of connection on the fixed structure 2 is located on the part of the front frame 3 in look at the front end of door 11.
  • the inverter of thrust 1 is linked and centered on the outer casing 18 of the turboshaft not shown by its front frame 3.
  • the locking device 20 first comprises a lock 25 consisting of a body 26 integral with the fixed structure 2, and a bolt 27 pivoting on the body 26 along the geometric axis 28.
  • the swivel bolt 27 comprises a fork 29 composed a notch 30 delimited on either side by a wing lower 31 and an upper wing 32.
  • the device for lock 20 then comprises a tie rod 35 secured to the door 11 at connection point 21, the free end 36 of said pulling 35 being in this example constituted by a roller pivotally mounted on the tie rod 35 along the geometric axis 37.
  • We will reference 38 the trajectory of the end of the tie rod 36 when the door pivots around its geometric axis referenced 14 in FIG. 1.
  • the front frame 3 can be twisted along 40, or the door pivots referenced 14 in FIG. 1 can be damaged, which can then cause displacement from gate 11 downstream 41 of the inverter 1.
  • This damage can therefore cause a distance of the free end 36 of the tie rod 35 relative to the latch 25, which has the effect of freeing the bolt 27 from the free end 36 of the tie rod 35 while the lock 25 is in perfect condition and in the closed position.
  • the free end 36 of the tie rod 35 tends to move according to a vector 42 turned towards said door pivots 11.
  • the hook 45 successively comprises a end 46 secured to the body 26 of the lock 25, a bottom 47 moving away from the body 26 of the lock 25, an upright 48, a free end 49 returning to the body 26 of the lock 25 and the front frame 3, and an opening 50 facing upwards between the free end of the hook 49 and the body 26 of the lock 25 or the front frame 3.
  • the bottom 47 is opposite the opening 50, and the path 38 of the free end 36 tie 35 goes through this opening 50 when the reverser 1 is not distorted.
  • the upper wing 32 of the bolt 27 closes the opening 50 of the hook 45, so that the free end 36 of the tie rod 35 is trapped inside 51 of the hook 45, which keeps said free end trapped 36 against latch 25 and prevents release of door 11 despite the damage suffered by the inverter 1.
  • the interior 51 of the hook 45 will be arranged and under its free end 49 a housing 52 at least at the size of the free end 36 of the tie rod 35.
  • this free end 36 arrives under the free end 49 of the hook 45 and is now retained by said free end 49 instead of upper wing 32 of the bolt 27, this bolt 27 thus being relieved of all solicitations.
  • the free end 49 of the hook 45 has a bearing face 55 facing the free end 36 of the tie rod 35 and substantially parallel to the path 38 from the free end 36 of the tie rod 35 in the closed position.
  • the support face 55 opposes this movement without cause side reaction on the free end 36 of the drawing 35, since it is substantially perpendicular to the vector 42, which avoids imposing stresses additional to upper wing 32 and lower wing 31 of the bolt 27.
  • the bearing face 55 also reduces these same solicitations in other cases of damage to the thrust reverser 1, the skilled person can also modify the orientation of said bearing face 55 in order to minimize these stresses according to the structure of the thrust reverser 1 and the damage it wants to ward off.
  • the bottom 47 of the hook 45 is in contact with the free end 36 of the tie rod 35 in the closed position, and the lower wing 31 of the bolt 27 is a little below the point of contact between the bottom 47 of hook 45 and free end 36 of tie rod 35, said bottom 47 thus acting as a limit stop for door 11, which discharges the lower wing 31 from bolt 27 of the stresses linked to the stop function of limit switch.
  • the bottom 47 of the hook 45 will be substantially perpendicular to the path 38 of the free end 36 of the tie rod 35, so as not to cause side reactions that should be taken up by door pivots referenced 14 in Figure 1, and optimize the locking force moment with respect to these pivots.
  • a self-closing lock 25 will be used whose bolt 27 has two stable positions, one open and the other closed, said bolt 27 being pulled towards either of these two positions by a spring 58 of which one end 59 is linked to the bolt 27 and the other end 60 to the body 26 of the lock 25, the spring 58 being on one side of the geometric pivot axis 28 of the bolt 27 when it is in the open position, said spring 58 passing on the other side of the pivot axis 28 of the bolt 27 when said bolt 27 goes into the closed position, a disengageable mechanism internal to the lock 25 immobilizing the bolt 27 in the closed position.
  • the free end 36 is a roller maintained by two tie rods 35 each acting at a end of the roller 36.
  • the hook 45 will have a width e1 greater than the width e2 of the bolt 27, the widths e1 and e2 being taken parallel to the axis geometric 37 of the free end 36 of the tie rod 35, said hook 45 comprising a slot 62 in which comes penetrate with limited clearance the end of the lower wing 31 of the bolt 27 in the closed position, said slot 62 passing through accordingly the free end 49 and the amount 48 of the hook 45.
  • slot 62 The function of slot 62 is to laterally hold the bolt 27 by its end when it is biased laterally that is to say parallel to its geometric axis 37, which makes it possible to discharge corresponding constraints the bolt 27 itself as well as its mechanism not shown for guiding and moving.
  • the upper wing 32 of the bolt 27 will penetrate also with limited play in slot 62, so improve the lateral retention of the bolt 27 by its end.
  • hook 45 includes housing 52 already describes and allows to receive the free end 36 of the pulling 35 under the free end 49 of the hook 45, this hook 45 being pivotally mounted on a hinge 65 integral with the body 26 of latch 25, said articulation 65 being arranged under the body 26 of the lock 25, said articulation 65 being substantially parallel to the geometric axis 37 of the end 36 of the tie rod 35.
  • the hook 45 extends on the other side of the articulation 65 by an arm 67 whose end 67a is linked to the body 26 of the lock 25 by a thermally element fuse 68.
  • the hook proper 45 is recalled against the lock 25 by at least one return spring 69, one of which end 69a is linked to the body 26 of the lock 25 and the other end 69b to hook 45.
  • the heat released melts the element thermally fusible 68.
  • the hook 45 is then released and pivots according to articulation 65 under the effect of the traction of the spring 69, which has the effect of bringing the free end 49 hook 45 above the free end 36 of tie rod 35 and as a result of retaining the door 11 in its position locked, even if the lock is accidentally opened 25.
  • housing 52 The function of housing 52 is in this case to allow also the tilting of the hook 45 under the effect of the tension of spring 69 without mechanical interference between the free end 36 of the tie rod 35 and said hook 45.
  • the latch 25 comprises a jack 26a secured to the body 26 of the lock 25, and used to actuate the bolt 27, this jack 26a extending at the rear of the lock 25. It in this case it is advantageous to lengthen the arm 67 and to tie its end 67a at the end of the bolt 26a by the link thermally fuse 68, in order to reduce the effort of traction to be supported by the thermally fusible element 68, and thus increase the ability of the hook 45 to retain door 11 in case of damage to the inverter 1. note that depending on the shape of the body 26 of the lock 25 and the relative position of arm 67, the thermally fusible element 68 can be stressed in tension as in the present case, but also in compression or shear.
  • the shape of the free end 49 of the hook 45 is such that the result of the contact efforts with the free end 36 of the tie rod 35 places the hook 45 in a locked and stable equilibrium position.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Special Wing (AREA)
  • Hinges (AREA)
  • Superstructure Of Vehicle (AREA)
  • Lock And Its Accessories (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP98400775A 1997-04-03 1998-04-02 Inverseur de poussée protégé au déverrouillage pour turbomoteur d'aéronef Expired - Lifetime EP0869272B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9704048A FR2761733B1 (fr) 1997-04-03 1997-04-03 Inverseur de poussee pour turbomoteur d'aeronef
FR9704048 1997-04-03

Publications (2)

Publication Number Publication Date
EP0869272A1 EP0869272A1 (fr) 1998-10-07
EP0869272B1 true EP0869272B1 (fr) 2004-06-23

Family

ID=9505463

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98400775A Expired - Lifetime EP0869272B1 (fr) 1997-04-03 1998-04-02 Inverseur de poussée protégé au déverrouillage pour turbomoteur d'aéronef

Country Status (6)

Country Link
US (1) US6145786A (ja)
EP (1) EP0869272B1 (ja)
JP (1) JPH10318043A (ja)
CA (1) CA2234437C (ja)
DE (1) DE69824657T2 (ja)
FR (1) FR2761733B1 (ja)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1236881B1 (en) * 2001-02-23 2005-05-18 Goodrich Actuation Systems Ltd Thrust reverser actuator lock mechanism
US6584763B2 (en) 2001-08-01 2003-07-01 Rohr, Inc. Lock for the translating sleeve of a turbofan engine thrust reverser
US6604355B1 (en) * 2001-08-31 2003-08-12 The Boeing Company Thrust reverser hook latch system
GB0505612D0 (en) * 2005-03-21 2005-04-27 Goodrich Actuation Systems Ltd Lock arrangement
US20110101158A1 (en) * 2005-03-29 2011-05-05 The Boeing Company Thrust Reversers Including Monolithic Components
US7690190B2 (en) 2005-05-11 2010-04-06 The Boeing Company Aircraft systems including cascade thrust reversers
US7559507B2 (en) * 2005-06-27 2009-07-14 The Boeing Company Thrust reversers including locking assemblies for inhibiting deflection
US7600371B2 (en) 2005-10-18 2009-10-13 The Boeing Company Thrust reversers including support members for inhibiting deflection
US8015797B2 (en) 2006-09-21 2011-09-13 Jean-Pierre Lair Thrust reverser nozzle for a turbofan gas turbine engine
US7946105B2 (en) * 2006-11-02 2011-05-24 Honeywell International Inc. Bi-directional locking ring assembly for aircraft thrust reverser manual drive unit
FR2920202B1 (fr) * 2007-08-20 2009-10-30 Aircelle Sa Systeme de commande d'au moins un actionneur de capots d'un inverseur de poussee pour turboreacteur
US8172175B2 (en) 2007-11-16 2012-05-08 The Nordam Group, Inc. Pivoting door thrust reverser for a turbofan gas turbine engine
US8051639B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser
US7735778B2 (en) 2007-11-16 2010-06-15 Pratt & Whitney Canada Corp. Pivoting fairings for a thrust reverser
US8091827B2 (en) 2007-11-16 2012-01-10 The Nordam Group, Inc. Thrust reverser door
US8052085B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US8052086B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser door
US8127530B2 (en) 2008-06-19 2012-03-06 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
FR2970521B1 (fr) * 2011-01-17 2013-01-04 Aircelle Sa Inverseur de poussee pour turboreacteur d'aeronef a nombre de verrous reduit
FR2991670B1 (fr) * 2012-06-12 2014-06-20 Aircelle Sa Inverseur de poussee a grilles retractables et tuyere variable
FR2998619B1 (fr) * 2012-11-28 2021-05-07 Aircelle Sa Verrou actif avec assistance de mobilisation et inverseur de poussee incorporant un tel verrou
US10267177B2 (en) 2015-02-09 2019-04-23 Rolls-Royce North American Technologies Inc. Turbine assembly having a rotor system lock
EP3168138B1 (en) * 2015-11-10 2018-06-06 Airbus Operations GmbH Aircraft door assembly
US10780987B2 (en) 2018-04-03 2020-09-22 Rohr, Inc. Fan cowl latch concept for fuselage mounted power plant
RU2726491C1 (ru) * 2019-09-05 2020-07-14 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Способ управления реверсивным устройством газотурбинного двигателя

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2780057A (en) * 1954-02-23 1957-02-05 Boeing Co Locks for jet thrust reversers
US4174128A (en) * 1977-07-18 1979-11-13 Caterpillar Tractor Co. Anti-rattle vehicle door latch mechanism
JPS6117154Y2 (ja) * 1980-06-18 1986-05-26
FR2488335B1 (fr) * 1980-08-11 1986-01-31 Snecma Dispositif detecteur de position d'un inverseur de poussee de turboreacteur et de son verrouillage
US5192023A (en) * 1988-10-27 1993-03-09 The Dee Howard Company Jet engine provided with a thrust reverser
US4966327A (en) * 1988-10-27 1990-10-30 The Dee Howard Company Jet engine provided with a thrust reverser
CA1326767C (en) * 1988-10-27 1994-02-08 Etienne Fage Jet engine provided with a thrust reverser
IL103190A (en) * 1991-09-25 1995-06-29 Messier Bugatti A security locking device that includes a movable hook
GB9215496D0 (en) * 1992-07-21 1992-09-02 Lucas Ind Plc Lock for an engine thrust reverser
GB9320447D0 (en) * 1993-10-05 1993-12-22 Lucas Ind Plc Lock for an engine thrust reverser
FR2712635B1 (fr) * 1993-11-19 1996-08-09 Hurel Dubois Avions Inverseur de poussée à portes pour moteur d'avion équipé de systèmes de sécurité interdisant l'ouverture intempestive des portes.
GB9418895D0 (en) * 1994-09-20 1994-11-09 Lucas Ind Plc Lock mechanism
EP0717184B1 (fr) * 1994-12-15 1999-10-06 The Dee Howard Company Inverseur de poussée à portes pivotantes mobiles en translation
EP0763654B1 (en) * 1995-09-13 1999-12-29 SOCIETE DE CONSTRUCTION DES AVIONS HUREL-DUBOIS (société anonyme) Electro/hydraulic system for a 2 door thrust reverser
GB2305460B (en) * 1995-09-25 1999-12-15 Dowty Boulton Paul Ltd Lock for engine thrust reverser

Also Published As

Publication number Publication date
DE69824657T2 (de) 2005-07-14
FR2761733B1 (fr) 1999-06-11
CA2234437C (fr) 2006-02-14
JPH10318043A (ja) 1998-12-02
CA2234437A1 (fr) 1998-10-03
DE69824657D1 (de) 2004-07-29
FR2761733A1 (fr) 1998-10-09
EP0869272A1 (fr) 1998-10-07
US6145786A (en) 2000-11-14

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